The invention relates to a seal for an aircraft incorporating a fire-resistant structure, and an aircraft incorporating at least one such a seal between structural elements of the aircraft connected to each other at a zone of the latter which may be a fire zone according to the standard ISO 2685:1998 or AC 20-135.

According to the invention, this seal (10) comprises: a seal body (11) at least partially elastomeric, the seal body defining at least one generally tubular or annular cavity (10A), and a fire-resistant structure (12) distinct from the seal body and disposed inside the cavity, the fire-resistant structure comprising an intumescent mass able to fill the cavity (10A) in an expanded state,
the intumescent mass being made of a rubber composition having an intumescence trigger temperature equal to or higher than 270° C., measured by a plane-plane rotary rheometer with a temperature scan from 23 to 380° C. according to a ramp of 10° C./min.

A system is disclosed for providing inerting gas to a protected space. The system includes an electrochemical cell including a cathode, an anode separated by a separator that includes an ion transfer medium, and an electrical connection to a power source or power sink. A cathode fluid flow path is in operative fluid communication with a catalyst at the cathode between a cathode fluid flow path inlet and a cathode fluid flow path outlet, and an anode fluid flow path is in operative fluid communication with a catalyst at the anode, and includes an anode fluid flow path outlet. A cathode supply fluid flow path is disposed between the protected space and the cathode fluid flow path inlet, and an inerting gas flow path is in operative fluid communication with the cathode flow path outlet and the protected space.

Provided are a battery tray and a power battery pack. The battery tray includes a tray body. The tray body includes a base plate, a side beam, and several partition plates, the side beam is disposed around the base plate and defines, together with the base plate, an accommodating space for battery cells. The partition plates are disposed on the base plate and divide the base plate into several regions for placing the battery cells. The partition plates and the side beam are each formed therein with an air passage and are in communication with each other. The partition plates are provided with several inlet vents, and the side beam is provided with at least one exhaust vent. The inlet vent is configured to introduce a flame, smoke or gas discharged from the battery cell into the air passage.

Provided are a battery tray and a power battery pack. The battery tray includes a tray body. The tray body includes a base plate, a side beam, and several partition plates, the side beam is disposed around the base plate and defines, together with the base plate, an accommodating space for battery cells. The partition plates are disposed on the base plate and divide the base plate into several regions for placing the battery cells. The partition plates and the side beam are each formed therein with an air passage and are in communication with each other. The partition plates are provided with several inlet vents, and the side beam is provided with at least one exhaust vent. The inlet vent is configured to introduce a flame, smoke or gas discharged from the battery cell into the air passage.

A thermal event detection and notification system detects a thermal event, a control unit receives information from, the information being indicative of the detected thermal event. The control unit determines, based on the information received, a location of said thermal event.

Various embodiments of the present invention provide a system and method for notifying a flight crew of a fire condition in a cargo container of an aircraft. For instance, particular embodiments involve installing at least one notification device on a cargo container that is in communication with at least one of a fire-detection system or a fire-suppression system for the cargo container. In these particular embodiments, the notification device is configured to emit energy when the fire-detection system detects the fire condition in the cargo container or the fire-suppression system activates as a result of the fire condition. Further, particular embodiments of the invention involve installing at least one detector positioned to detect the energy emitted by the notification device. In these particular embodiments, the detector is configured to send a signal to notify the flight crew of the fire condition after detecting the energy emitted by the notification device.

Various embodiments of the present invention provide a system and method for notifying a flight crew of a fire condition in a cargo container of an aircraft. For instance, particular embodiments involve installing at least one notification device on a cargo container that is in communication with at least one of a fire-detection system or a fire-suppression system for the cargo container. In these particular embodiments, the notification device is configured to emit energy when the fire-detection system detects the fire condition in the cargo container or the fire-suppression system activates as a result of the fire condition. Further, particular embodiments of the invention involve installing at least one detector positioned to detect the energy emitted by the notification device. In these particular embodiments, the detector is configured to send a signal to notify the flight crew of the fire condition after detecting the energy emitted by the notification device.

An onboard electrochemical system of an electrochemical cell including a cathode and an anode separated by an electrolyte separator is selectively operated in either of two modes. In a first mode of operation, water or air is directed to the anode, electric power is provided to the anode and cathode to provide a voltage difference between the anode and the cathode, and nitrogen-enriched air is directed from the cathode to an aircraft fuel tank or aircraft fire suppression system. In a second mode of operation, fuel is directed to the anode, electric power is directed from the anode and cathode to one or more aircraft electric power-consuming systems or components, and nitrogen-enriched air is directed from the cathode to a fuel tank or fire suppression system.

An onboard electrochemical system of an electrochemical cell including a cathode and an anode separated by an electrolyte separator is selectively operated in either of two modes. In a first mode of operation, water or air is directed to the anode, electric power is provided to the anode and cathode to provide a voltage difference between the anode and the cathode, and nitrogen-enriched air is directed from the cathode to an aircraft fuel tank or aircraft fire suppression system. In a second mode of operation, fuel is directed to the anode, electric power is directed from the anode and cathode to one or more aircraft electric power-consuming systems or components, and nitrogen-enriched air is directed from the cathode to a fuel tank or fire suppression system.

A nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer air flow path, and a core conduit defined radially inward from the inner gas flow path. An injector assembly includes an outer housing, a nozzle within the outer housing, and an outer housing gas flow path defined radially outward from the nozzle between an inner surface of the outer housing and an outer surface of the nozzle. The nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path and a core conduit defined radially inward from the inner gas flow path.